Summary The de Havilland DHC-8 aircraft (registration C-FGRP, serial number207) was being operated by Jazz Air Inc. as flight number JZA7841from Kingston, Ontario, to Toronto/LesterB. Pearson International Airport, Ontario. The aircraft departed Kingston at 1403 eastern standard time with the first officer, in the right seat, designated as the pilot flying. During the initial climb following take-off, the first officer noted that abnormal forward pressure on the control column was required to keep the aircraft from pitching nose up. To counter the pitch-up, he trimmed the aircraft nose down. Thirty seconds after becoming airborne, the aircraft was 350feet above ground level (approximately 700feet above sea level (asl)) and the first officer had applied full nose-down trim. The amount of forward pressure on the control column continued to increase as the aircraft accelerated, and the first officer notified the captain of the control difficulties and requested his assistance in holding the control column forward. As the aircraft climbed, the captain declared an emergency, indicating that they were experiencing control difficulties and that the aircraft may have to land at Trenton, Ontario. The flight crew levelled the aircraft at 4000feet asl and pulled the elevator pitch disconnect handle, isolating the left and right elevators. The captain's elevator control functioned normally after the disconnect, and he decided to continue the flight. The flight crew conducted a flapless landing at Toronto without further incident. Ce rapport est galement disponible en franais. Other Factual Information History of the Flight The flight crew members had spent the night in Kingston and were waiting at the airport when the aircraft arrived. This was their first flight of the day, although the aircraft had already flown this day on four prior flights by three different flight crews. The captain conferred with the incoming captain, while the first officer conducted the preflight inspection of the aircraft. There were no reported flight control anomalies on the previous flight, and there was nothing out of the ordinary noted by the first officer during his inspection. The turn-around time in Kingston was approximately 15minutes. During the take-off run, at about 1430 eastern daylight time,1 the controls were lighter than normal, and at rotation, almost no nose-up force was required. As the aircraft became airborne and accelerated, increasing forward pressure on the control column was required to maintain the proper climb attitude, even with full nose-down trim. The flight crew members assessed that there was a pitch control anomaly, not a jammed elevator control or load shift. They were still able to control the aircraft and maintain the correct climb attitude and so they continued with normal climb procedures. The aircraft was levelled off at the assigned altitude of 4000feet asl, the flaps were retracted, and the aircraft was allowed to accelerate. The crew reviewed the Air Canada Jazz Quick Reference Handbook(QRH) and the Abnormal/Emergency Procedures section of the Dash8 Standard Operating Procedures (SOP). Although they had previously assessed that the elevator control was not jammed, they decided that the pitch control jam procedure was the most appropriate for their circumstance. The aircraft was slowed from 185to 150knots indicated airspeed (KIAS), the maximum speed for a jammed pitch control. The pitch disconnect was pulled, and the left-side elevator controls became free and functioned normally. The captain assumed control of the aircraft and climbed to 12000feet asl in the vicinity of Trenton and decided to continue to Toronto. When the aircraft was inspected after landing, half of one of the balance weights from the right-side elevator spring tab, and the two nuts that secure it were missing. The two bolts had migrated out of the remaining half weight and jammed on the top surface of the elevator, holding the elevator spring tab in the trailing-edge-down position. Pitch Control System The DHC-8 pitch control system consists of two elevator control cable circuits, each operating an independently mounted, spring tab-assisted elevator. Each elevator has a spring tab at the inboard end and a trim tab at the outboard end. The left elevator is actuated by the captain's control column through the left cable control circuit and the left elevator spring tab system. The right elevator is actuated by the first officer's control column through similar components. The two control columns are normally interconnected to provide simultaneous movement of both elevators, but the control columns can be disconnected by a pitch disconnect system if one of the control cable circuits jams. This frees the unjammed circuit and allows it to operate through its normal range. Elevator Spring Tab Operation The spring tab system for each elevator is designed to provide aerodynamic assistance to elevator movement. There are two mass balances extending forward of each spring tab leading edge (seeFigure1). Each mass balance assembly consists of two weights bolted together and secured to the arm with two bolts. Figure1. Elevator spring tab and balance weights When the elevators are actuated, the control column movements go directly to the spring tab and then to the elevator through the torque shaft (see Figure2, item3). With the airplane on the ground and no aerodynamic load, the stiffness of the torque shaft overcomes the weight of the elevator, causing it to move with the control column. The geometry of the actuating hardware causes the elevator to move in the opposite direction to the spring tab. Maximum spring tab deflection is limited by the crank stops (Figure2, item8), after which the elevators are moved directly by the control column. Maximum elevator deflection is limited by the lever stops (Figure2, item12). The flight data recorder showed that the two elevators were moving approximately in sync with each other until the aircraft was accelerating on the take-off run. The maximum differential in elevator deflection was reached when the airspeed was at approximately 120KIAS; the right elevator was approximately 12trailing edge up and the left elevator was approximately 8trailing edge down. According to calculations completed after the occurrence, at 185KIAS, the stress on the tail was close to its structural limit, and a specific, one-time maintenance inspection was designed to look for additional damage. Maintenance History Between 22July and 07August2004, the aircraft had been at the Air Canada paint shop in Toronto to be repainted. The aircraft accumulated approximately 162hours of flight time and 162cycles between the time this maintenance was completed and the occurrence flight. The maintenance work package Preparation for Aircraft Paint Visit had three sections. The first section covered the preparation of the aircraft for painting. This section included items such as draining the toilet, disconnecting the batteries, and removing the static wicks. These items were completed on 22July2004. The second section was the painting check sheet. The third section was the return to service section. This section included items such as reconnecting the batteries, servicing the lavatories, balancing the control surfaces and tabs, checking that control movements were free and clear, conducting a L(line) check, and conducting a full-power engine run. This section required two signatures to signify its completion. One signature, dated 08August2004, signified that an independent inspection of the flight controls had been completed. The other signature, dated 09August2004, signified that all the work had been completed properly. When the right elevator spring tab was checked, it was nose heavy and required rebalancing. This work was not noted on the check sheets. Checking the balance of the elevator spring tab is accomplished by disconnecting the tab drive bracket (Figure2, item6) from the pushrod (Figure2, item7) and attaching a specific weight to the trailing edge of the tab. The rebalancing was accomplished by removing the steel balance weights and grinding some material from the upper surface of the weights. Because this is work that disturbs engine or flight controls as specified in Section571.10 of the Canadian Aviation Regulations (CARs), there is a requirement for an independent inspection. The independent inspection was carried out the following morning. Maintenance crews were brought in from Halifax, Nova Scotia, to return the aircraft to service. On 07August2004, the aircraft maintenance engineer (AME) who balanced the spring tab started his normal work shift in Halifax at 0700 Atlantic daylight time, and that morning was asked to go to Toronto to work on the aircraft coming out of the paint shop. He arrived in Toronto in the afternoon, and began working on C-FGRP. Late at night on 07August2004, he completed the removal and reinstallation of the weights from the spring tab balance arm. The AME who conducted the independent inspection of the controls arrived from Halifax on the evening of 07August2004, and the first task he completed the following morning was the independent inspection of all the aircraft flight controls. Training in Emergency Procedures Part of the DHC-8 pilot recurrent training involves dealing with flight control jams. In a DHC-8 flight simulator, pilots are routinely given a situation where the elevator control is jammed and will not move. The training is designed to familiarize the pilots with the QRH procedures, to practice pulling the elevator disconnect, and to fly the aircraft using the unjammed elevator control circuit. The training does not include a jammed spring tab scenario. The SOPs include emergency procedures for pitch control jam, elevator control and trim malfunction, and manual elevator trim failure. The pitch control jam procedure from the SOPs is stated below. (19) Pitch Control Jam On recognizing a jam in the elevator control circuit, both pilots will attempt to overcome the jam with firm elevator pressure. If unable to obtain elevator control the PF will call for relax pressure and pull and rotate the PITCH DISCONNECT HANDLE 90degrees. The pilot with the free control wheel will call Mycontrol. Note: The PF may command the PNF to pull the pitch handle if required. If the jam occurs below level off height, at level off height the PF will command the PNF to leave the flaps alone and set climb power. The PNF will disarm the autofeather, select the taxi and approach lights off, select ignition normal if appropriate, turn the bleeds on and set climb power. Through 1000feet HAA2 the PF will request the Emergency Checklist followed by the After Takeoff Check. Caution: Do not engage the autopilot and do not exceed 150KIAS or speed at which jam occurred whichever is greater. WARNING: IF CLOSE TO THE GROUND OR AIRCRAFT CONTROL IS IN JEOPARDY, CONSIDERATION SHOULD BE GIVEN TO IMMEDIATELY ACTIONING THE PITCH DISCONNECT VERSUS PUSHING OR PULLING.